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UID:0-213@aerospace.technion.ac.il

DTSTART;TZID=Asia/Jerusalem:20220425T133000

DTEND;TZID=Asia/Jerusalem:20220425T143000

DTSTAMP:20230403T122301Z

URL:https://aerospace.technion.ac.il/events/wing-dynamic-shape-sensing-fro
 m-fiber-optic-strain-data-using-the-kalman-state-estimator/

SUMMARY:Wing Dynamic Shape-Sensing From Fiber-Optic Strain Data Using the K
 alman State Estimator
DESCRIPTION:Lecturer:Tsoof Joels\n Faculty:Department of Aerospace Engineer
 ing\n Institute:Technion – Israel Institute of Technology\n Location:Cla
 ssroom 165\, ground floor\, Library\, Aerospace Eng. & https://technion.zo
 om.us/j/92528464038\n Zoom: \n Abstract: \n Details: \n New aircraft desig
 ns are more flexible than ever before\, making them susceptible to adverse
  aeroelastic phenomena such as a large dynamic response to atmospheric tur
 bulence and even flutter. On the other hand\, some studies suggest that wi
 ng flexibility can be leveraged to achieve optimal performance. This motiv
 ated the aeroelastic community to develop methods for sensing the deformed
  shape of flexible wings in-flight. The current research study proposes a 
 novel method for shape sensing that is based on strain data\, an aeroelast
 ic model\, and the use of the Kalman state estimator.\nSeveral recent stud
 ies proposed different methods in which strain data\, measured in optical 
 fibers\, can be used to estimate the deformed shape of a flexible wing. Fi
 ber optic sensors typically provide accurate\, high-resolution strain data
 \, yielding accurate estimates of a wing's deformed shape. However\, the s
 train data could be imperfect (for example\, due to saturation or temperat
 ure effects)\, corrupted\, or missing. The current study proposes to use a
  Kalman state estimator that weighs strain data and simulation output of a
 n aeroelastic model to estimate wing deformations. The method is demonstra
 ted in a wind-tunnel test of a flexible wing model excited by prescribed c
 ontrol surface deflections. Fiber Bragg Grating sensors embedded in two op
 tical fibers over the wing's span measure strains\, which are used to esti
 mate the wing deformations. The latter are compared to wing deformations m
 easured by a motion recovery camera system. Results show the advantages of
  the proposed method when the strain data or the aeroelastic model are imp
 erfect. Additionally\, the method provides  smooth estimates of the modal
  velocities readily available for use by the vehicle's control system.
CATEGORIES:Seminars
LOCATION:Classroom 165\, ground floor\, Library\, Aerospace Eng. & https://
 technion.zoom.us/j/92528464038

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